Abstract

A computational procedure is proposed to determine effective constitutive relations for composite laminates with progressive cracking. The procedure is based on the assumption that the effective stiffness of a cracked ply in a laminate can be determined by analyzing the cracked ply by itself independent of the rest of the laminate. A polynomial failure criterion is used to predict ply cracking using effective ply stresses. The procedure provides a full set of effective laminate stiffnesses as well as crack densities in constituent plies.

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